Application of simplified three-equation transition model in hypersonic flow

CAI Linfeng; LI Haoge; ZHAO Wenwen; CHEN Weifang

doi:10.7638/kqdlxxb-2017.0172

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Application of simplified three-equation transition model in hypersonic flow

更新时间：2026-05-28

- Application of simplified three-equation transition model in hypersonic flow
- Vol. 37, Issue 6, Pages: 945-949(2019)
- 作者机构：
  
  浙江大学航空航天学院,浙江,杭州,310027
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2017.0172
  CLC： V211.3
- Published：2019
- 稿件说明：
移动端阅览
蔡林峰, 李昊歌, 赵文文, 陈伟芳. 简化三方程转捩模型在高超声速流动中的应用[J]. 空气动力学学报, 2019, 37(6): 945-949.

CAI Linfeng, LI Haoge, ZHAO Wenwen, et al. Application of simplified three-equation transition model in hypersonic flow[J]. 2019, 37(6): 945-949.
蔡林峰, 李昊歌, 赵文文, 陈伟芳. 简化三方程转捩模型在高超声速流动中的应用[J]. 空气动力学学报, 2019, 37(6): 945-949. DOI： 10.7638/kqdlxxb-2017.0172.

CAI Linfeng, LI Haoge, ZHAO Wenwen, et al. Application of simplified three-equation transition model in hypersonic flow[J]. 2019, 37(6): 945-949. DOI： 10.7638/kqdlxxb-2017.0172.

摘要

在雷诺平均方法的基础上，通过耦合

k-ω

SST湍流模型和间歇因子转捩模型，引入湍流模型和转捩模型的可压缩修正方法，对高超声速平板、双楔、尖锥三类模型边界层转捩流动开展了数值模拟研究。与实验结果的对比分析表明基于压力梯度表征参数

Ω/ω

的简化三方程转捩模型，能够准确捕捉高超声速平板边界层流动的转捩起始位置、转捩区域长度以及湍流区壁面热流。而对于双楔、尖锥模型，改进前的简化三方程转捩模型由于受到流动可压缩效应的影响，边界层转捩后湍流区的壁面热流模拟预测结果明显高于实验值。在添加模型可压缩修正方法后，转捩区域长度和湍流区壁面热流模拟结果得到有效改善，与实验值吻合较好。可见，简化三方程转捩模型在添加可压缩修正方法后具备准确模拟预测高超声速边界层流动转捩的潜力。

Abstract

On the basis of the RANS model

the numerical simulation study of hypersonic boundary-layer transitional flow was carried out on a flat-plate

a double wedge

and a cone by modifying

k-ω

SST turbulence model and the intermittency transition model with compressibility correction. Based on the comparison with experimental result

it is shown that the simplified three-equation transition model based on the pressure gradient characterization parameter

Ω/ω

can correctly catch the transition onset location

the length of transition region

and the turbulent z

one heat flux on the wall for the flat-plate hypersonic boundary-layer flow. For the double wedge and cone case

the wall heat flux in turbulent zone calculated by the simplified three-equation transition model is much higher than the experimental data due to the flow compression effects. However

it can agree well with the experimental data after adding compressibility correction to the model. The simplified three-equation transition model with appropriate compressibility correction has potential to simulate hypersonic boundary-layer transitional flow correctly.

关键词

Keywords

references

LEYLEK J H, WALTERS D K. A new model for boundary layer transition using a single-point RANS approach[J]. Journal of Turbomachinery, 2002, 126(1):193-202.

WANG L, FU S. A new transition/turbulence model for the flow transition in supersonic boundary layer[J]. Chinese Journal of Theoretical and Applied Mechanics, 2009, 41(2): 162-168. (in Chinese)

WANG L, FU S, CARNARIUS A, et al. A modular RANS approach for modelling laminar-turbulent transition in turbomachinery flows[J]. International Journal of Heat Fluid Flow, 2012, 34(4):62-69.

LANGTRY R B, MENTER F R. Correlation-based transition modeling for unstructured parallelized computational fluid dynamics codes[J]. AIAA Journal, 2009, 47(12): 2894-2906.

MALAN P, SULUKSNA K, JUNTASARO E. Calibrating the γ - Re θt transition model for commercial CFD[C ] //47th AIAA Aerospace Sciences Meeting, 2009: 5-8.

WANG G, LIU Y, WANG G Q, et al. Transitional flow simulation based on γ - Re θt transition model[J ] . Acta Aeronautica et Astronautica Sinica, 2014, 35(1): 70-79. (in Chinese)

KAYNAK Ü. Supersonic boundary-layer transition prediction under the effect of compressibility using a correlation-based model[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2012, 226(7): 722-739.

CRAY C, NICHOLS R, NEROORKAR K, et al. Validation and assessment of turbulence transition models[C]//47th AIAA Aerospace Sciences Meeting and Exhibit, 2009.

KONG W X, YAN C, ZHAO R. γ - Re θt model research for high-speed boundary layer transition[J ] . Acta Aerodynamica Sinica, 2013, 31(1):120-126.

ZHANG X D, GAO Z H. Numerical discuss to complete empirical correlation in Langtry's transition model[J]. Applied Mathematics and Mechanics, 2010, 31(5):544-552. (in Chinese)

ZHANG Y F, HE K, ZHANG Y R, et al. Improvement and validation of menter's transition model for hypersonic flow simulation[J]. Journal of Astronautics, 2016, 37(4): 397-402. (in Chinese)

ZHENG Y, LI H Y. Application of γ-Re θ transition model in hypersonic flow based on new correlation equation[J ] . Journal of Propulsion Technology, 2015, 36(6): 839-845. (in Chinese)

ZHOU L, YAN C, KONG W X. Numerical simulation of forced boundary layer transition on hypersonic vehicleforebody[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(6): 1487-1495. (in Chinese)

XIA C, CHEN W. Boundary-layer transition prediction using a simplified correlation-based model[J]. Journal of Aeronautics, 2016, 29(1):66-75.

CODER J, MAUGHMER M. One-equation transition closure for eddy-viscosity turbulence models in CFD[C]//50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition Nashville, 2012.

WILCOX D C. Turbulence modeling for CFD[M]. CA: DCW industries La Canada, 1998.

MEE D J. Boundary-layer transition measurements in hypervelocity flows in a shock tunnel[J]. AIAA Journal, 2002, 40(8): 1542-1548.

FRAUHOLZ S, REINARTZ B U, MÜLLER S, et al. Transition prediction for scramjet intakes using the γ - Re θt model coupled to two turbulence models[J ] . Journal of Propulsion and Power, 2014: 1-19.

MACLEAN M, MUNDY E, WADHAMS T, et al. Comparisons of transition prediction using PSE-chem to measurements for a shock tunnel environment[R]. AIAA 2007-4490.

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

CKDO one-equation RANS simulation on transition of hypersonic cross flow

Research on helicity modification turbulence model based on the AENS simulation platform

Uncertainty quantification of Menter SST turbulence model coefficients in hypersonic flow simulations

Flow quality analysis and improvement of hypersonic nozzle

Three-channel coupled instability criteria for symmetrical tailless hypersonic vehicles

Related Author

WANG Hao

XU Jinglei

LIU Yangwei

LI Bin

TANG Yumeng

CAO Jie

LUO Pengzhong

YE Zhengyin

Related Institution

School of Energy and Power Engineering, Beihang University, Beijing

School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai

School of Aviation, Hangzhou Innovation Institute (Yuhang), Beihang University, Hangzhou

Computational Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang

Research Institute of Aero-Engine, Beihang University, Beijing

AI问答

⁰